Abstract: A latching mechanism removably attaches an accessory to an offroad vehicle without requiring tools. The latching mechanism includes a body, a shaft extending through the body, and a handle riding on a conical surface of the body for rotating the shaft relative to the body. An oblong head extends on a lower side of the body, rotatable by the handle and shaft to a position where the head extends under a shoulder of a mounting recess. A spring system biases the head axially, such that the head can be moved either upwardly or downwardly from a balanced elevation set by a nut tightenable on a bolt. The mounting recess has an upper portion shaped differently from a lower portion. The body includes a hooking portion which extends significantly above the top of the mounting recess.

Abstract: The disclosure provides a control device capable of smoothly performing a turning operation due to an external force for a mobile body having a movement operation part and a seat part of occupant. A control device which performs a movement control of movement operation parts a mobile body estimates a movement rotational force in the yaw direction according to a movement of the mobile body and a rotational driving force in the yaw direction according to a driving forces of an actuator, and estimates an external force rotational force, which is a rotational force in the yaw direction due to an external force applied to the mobile body, based on these estimation values. A turning operation of the mobile body is performed according to an estimation value of the external force rotational force and a maneuver operation of the mobile body.

Abstract: A two-wheeled vehicle includes a frame assembly having a front end and a rear end extending along a longitudinally-extending centerline, a front ground-engaging member operably coupled to the front end of the frame assembly at a front rotational axis, and a rear ground-engaging member operably coupled to the rear end of the frame assembly at a rear rotational axis. The vehicle further includes an engine supported by the frame assembly and operably coupled to the front and rear ground-engaging members, and the engine includes a throttle body assembly. Additionally, the vehicle includes an air intake assembly fluidly coupled to the engine and including an airbox and a mounting plate having a first channel and a second channel. The first and second channels are configured to align with the throttle body assembly. The mounting plate is configured to couple the airbox to the throttle body assembly.

Abstract: An embodiment personal mobility includes a main body provided in a box shape, a steering device comprising a steering handle configured to extend outwardly from the main body or to retract so as not to protrude from the main body, and a front wheel and a rear wheel installed on a front side and a rear side of the main body, respectively.

Abstract: A throttle grip device controls an engine of a vehicle in accordance with a rotation angle of a throttle grip detected by a rotation angle detection unit, a base end portion of the throttle grip has a first flange region portion and a second flange region portion formed over a predetermined range in a circumferential direction, the first flange region portion and the second flange region portion are respectively formed at positions offset by a predetermined dimension with respect to an axial direction of the throttle grip, and the first support portion and the second support portion are formed so as to protrude at positions corresponding to the first flange region portion and the second flange region portion, respectively.

Abstract: A leaning vehicle includes a vehicle body, a left front wheel, a right front wheel, a lean mechanism, and a lean brake mechanism. The lean mechanism causes the left front wheel and the right front wheel to lean about a front-rear direction as a rotation center when the vehicle body leans about the front-rear direction as a rotation center. The lean brake mechanism brakes a leaning operation of the lean mechanism. The lean brake mechanism includes a brake disc and brake pads. The brake disc is attached to an upper arm or a lower arm. The brake pads, which are attached such that their position relative to the brake disc changes in the leaning operation, produce a frictional force against the brake disc in the leaning operation.

Abstract: Provided is an intelligent electric wheel hub which belongs to the field of bicycle parts. Two ends of a cylindrical wheel hub housing (2) of the electric wheel hub are respectively connected to a wheel hub left end cover (25) and an outer flywheel ring (7) of a flywheel mechanism to form an inner cavity for integrating and accommodating a gear motor, a battery pack and a controller panel. The intelligent electric wheel hub is highly integrated and is energy-saving and environmentally friendly.

Abstract: A rear derailleur of a bicycle includes a fixing portion connected to a frame of the bicycle, a linkage assembly pivotally connected to the fixing portion, a moving portion pivotally connected to the linkage assembly, a chain guide assembly connected to the moving portion, a driving assembly, a rechargeable battery for providing an electrical energy required for the motor, a coil, and a wireless charging circuit for receiving an electric power of the coil for charging the rechargeable battery. The driving assembly includes a motor including and a driving gear assembly connected to the linkage assembly. The motor includes an output shaft for driving the driving gear assembly and for driving the linkage assembly to pivot via the driving gear assembly, thereby to drive the moving portion and the chain guide assembly to move. The coil receives an external charging power and is disposed on the fixing portion, the moving portion, or the linkage assembly.

Abstract: A belt tensioner for use with a bike is provided. The bike includes a frame and a belt. The frame includes a chain stay and a seat stay having a top surface and bottom surface. The belt tensioner includes a tensioner skeleton, a roller and a tension regulator. The tensioner skeleton is pivotally connected to the chain stay or the seat stay. An included angle is formed between the tensioner skeleton and chain stay or the seat stay. The roller is pivotally connected to the tensioner skeleton and in contact with the belt. The tension regulator presses against the belt to adjust tension of the belt. The tension regulator is disposed at an end of the tensioner skeleton, and the end of the tensioner skeleton is positioned distal to the bottom surface.

Abstract: A lifesaving handle system for a watercraft surface such as, but not limited to, a boat hull. The handle system remains inside a cavity in an exterior surface of a watercraft hull when the watercraft is upright (i.e., when it is not capsized) such as when it is flowing on a body of water in normal operation. The handle may be rotatably attached to an interior surface of the cavity such that when the boat is upright, as in non-capsized operation, the handle hangs vertically in the closed cavity and is not within the flow of water passing along and around the watercraft hull when the boat is motivated on a body of water; and when the boat is overturned or capsized, the handle rotates out from the closed cavity under the force of gravity such that the grip handle is presented to a person in the water.

Abstract: The structure comprises a hull extending longitudinally along a longitudinal hull axis, a mooring equipment, comprising a first group of mooring lines connected to an anchor on the bottom of the body of water, the mooring lines of the first group protruding laterally beyond a first side of the hull, opposite the second side of the hull. The mooring equipment comprises a second group of mooring lines protruding laterally beyond the second side, and connected to an anchor located away from the second side on the bottom of the body of water. The mooring lines of the first group are connected on the first side of the hull, the space facing a second lateral wall of the hull being free of mooring lines.

Abstract: Various implementations include a sports board storage device. The device includes a housing, one or more linkages, a foot, and one or more linkage members. The housing has a first prong and a second prong. The one or more linkages are pivotably coupled to the first prong. The foot is pivotably coupled to the one or more linkages. The one or more linkage members are coupled to at least one of the one or more linkages. The one or more linkage members are movable relative to the housing to cause rotation of the one or more linkages and to cause the foot to move between a retracted position and an extended position. The foot is closer to the second prong in the extended position than it is in the retracted position.

Abstract: A gyroscopic roll stabilizer includes an enclosure, a flywheel assembly, a bearing, a motor, and a bearing cooling circuit. The enclosure is mounted to a gimbal for rotation about a gimbal axis and configured to maintain a below-ambient pressure. The flywheel assembly includes a flywheel and flywheel shaft. The bearing rotatably mounts the flywheel assembly inside the enclosure for rotation about a flywheel axis. The bearing has an inner race and an outer race. The inner race is affixed to the flywheel shaft, and the outer race is held rotationally fixed relative to the enclosure. The motor is operative to rotate the flywheel assembly. The bearing cooling circuit is configured to transfer heat away from the bearing by recirculating cooling fluid along a closed fluid pathway. The gyroscopic roll stabilizer is configured to transfer heat away from the inner and/or outer race of the bearing to the cooling fluid.

Abstract: A gyroscopic roll stabilizer comprises a gimbal having a support frame and enclosure configured to maintain a below-ambient pressure, a flywheel assembly including a flywheel and flywheel shaft, one or more bearings for rotatably mounting the flywheel inside the enclosure, a motor for rotating the flywheel, and bearing cooling system for cooling the bearings supporting the flywheel. For smaller units, the bearing cooling system is effective to enable a flywheel with a moment of inertia less than 40,000 lb in2 to be accelerated at a rate of 5 rpm/s or greater. For larger units, the bearing cooling system is effective to enable a flywheel with a moment of inertia greater than 40,000 lb in2 to be accelerated at a rate of 2.5 rpm/s or greater.

Abstract: A portable marine anchoring device maximizes holding capacity while anchored into the bottom of a body of water and a portable and foldable fender capable of being securely fastened to a vessel to prevent it from being dislodged over time.

Abstract: A ship body control device is provided, which includes a sensor, a propelling force controller, and an autopilot controller. The sensor measures a speed of a ship. The propelling force controller controls a propelling force of the ship. The autopilot controller outputs an instruction to reduce the propelling force to the propelling force controller, when a condition of canceling an automatic cruise in which the speed of the ship matches with an automatic ship speed setting is satisfied.

Abstract: A life preserver includes first and second buoyancy sections 3, 4 arranged such that, in use, the first and second buoyancy sections lie on opposite sides respectively of a wearer's chest, wherein said first and second buoyancy sections include respective inner facing regions that face one another above the wearer's chest, each of the facing regions having a chin support portion 11A, 11B and being configured to abut each other in use to form a chin support.

Abstract: A swim aid device comprising a belt having a hoop portion including a first tab and a second tab, a front end and a back end opposite said front end wherein the back end includes an opening and wherein the belt is biased in a first closed position and operatively openable to a second open position; and one or more buoyant elements couplable to said back end of the belt and securable in place with said tabs wherein a buoyancy of the one or more buoyant elements allows a user to remain afloat.

Abstract: The present application relates to power transmission system used in marine engines and in particular to a divided gear wheel (11, 12), for a power transmission system 1,2, used in marine engines, to a power transmission system used in marine engines to a method to operate said power transmission system and to a marine engine comprising a power transmission system.

Abstract: A stowable propulsion device for a marine vessel. A base is configured to be coupled to the marine vessel. A propulsor is configured to propel the marine vessel in water. An arm pivotably couples the propulsor to the base to move the propulsor into and between a stowed position located proximate to the marine vessel and a deployed position located relatively distal from the marine vessel as compared to the stowed position. An actuator linkage includes a first link that is pivotably coupled to the base and a second link that pivotably couples the first link to the arm. An actuator pivots the actuator linkage to move the propulsor into and between the stowed position and the deployed position.

Abstract: A method for making a pressure bulkhead assembly of an aircraft includes determining first locations and first orientations of a plurality of first holes, pre-drilled in an aft pressure bulkhead. The method also includes determining a first surface profile of a first interface surface of the aft pressure bulkhead and determining a second surface profile of a second interface surface of each one of a plurality of splice angles. The method also includes determining second locations and second orientations of a plurality of second holes to be drilled in each one of the plurality of splice angles corresponding to the plurality of first holes in the aft pressure bulkhead and drilling the plurality of second holes in each one of the plurality of splice angles at the second locations and second orientations.

Abstract: Phased array antennas, such as a multi-function aperture, are limited in performance and reliability by traditional air-cooled thermal management systems. A fuel-cooled multi-function aperture passes engine fuel through heat exchangers that surround the multi-function aperture to provide better heat transfer than can be achieved through air cooling systems. The increased heat transfer and thermal management results in a multi-function aperture with improved performance and reliability.

Abstract: A motor assembly that includes a motor having a motor casing, a rotatable shaft extending from said motor casing to a shaft length and a hub coupled to said rotatable shaft, the hub having a circumferential skid surface disposed immediately proximal to the motor casing and having a channel configured to seat a propeller, when a propeller is present, wherein a bending moment applied to the shaft through the hub results in the circumferential skid surface contacting said motor casing.

Abstract: The present disclosure provides a rotating propeller design that maintains a high efficiency and reduces noise. The design provides an unloaded tip zone of positive lift starting prior to an end of the tip with negligible, if any, positive lift that is counterintuitive to the purpose of a propeller. The unloaded tip zone decreases the strength of a tip vortex and reduces induced drag. The result is a significant reduction in noise while maintaining substantially high mechanical efficiency, even with an optional increase in RPM to compensate for the reduced lift without requiring a longer propeller. At least one propeller design can break the beta angle from the propeller hub with a different beta angle at a first location from the hub and then also break the beta angle at a second location further from the hub into the unloaded tip zone to form a double break propeller.

Abstract: An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; —a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.

Abstract: An aerodynamic element includes at least one first, fixed aerodynamic part including a box section that is covered at least partly by a plate with an extreme part, and one second aerodynamic part including a peripheral surface with an end and at least one holding element provided with a shoulder which forms, with the extreme part of the plate, a groove in which the end of the peripheral surface can be housed, such that the peripheral surface and the plate form a junction having an ascending profile. The presence of the groove makes it possible to obtain a continuous ascending junction with favors a laminar airstream on the upper surface of the aerodynamic element.

Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine rotatably coupled to a nacelle. The multi-segment chine includes at least two segments. The at least two segments include a first segment and a second segment. The first segment and the second segment are independently rotatable relative to the nacelle about an axis of rotation.

Abstract: A levered landing gear including a first shock strut having and a second shock strut disposed concentrically with the first shock strut. The second shock strut includes a metering pin coupled to a mounting surface of a piston of the second shock strut, and an orifice plate that cooperates with the metering pin to meter an amount of fluid flow as the second shock strut is compressed. The metering pin includes flutes longitudinally arranged on the metering pin between first and second ends of the metering pin, the flutes having a varying depth so that a fluid flow through the flutes is greater at the second end than fluid flow through the flutes at the first end. A truck lever is coupled to both the first shock strut and the second shock strut such that the second shock strut pivots the truck lever relative to the first shock strut.

Abstract: Aircraft wheel and brake assembly, including: a wheel (20) and a brake (21) comprising at least one friction member (31), an actuator bracket (24), and at least one brake actuator (25) held by the actuator bracket; a first measuring device arranged to measure a rotation speed of the wheel (20); a second measuring device arranged to measure a temperature of the friction member (31); a data concentrator (40) arranged to acquire measurement signals produced by the first measuring device and by the second measuring device, and to process and transmit the measurement signals to the outside, the data concentrator (40) being mounted on the actuator bracket (24).

Abstract: A rotorcraft has a drive system including a main rotor coupled to a main rotor gearbox to rotate the main rotor at a rotor speed, a main engine coupled to the drive system to provide a first power, a supplemental engine coupled, when a first clutch is engaged, to the drive system to provide a second power additive to the first power, and a control system operable to control the main engine and the supplemental engine to provide a total power demand, where the main engine is controlled based on variations in rotor speed and a power compensation command to produce the first power, and the supplemental engine is controlled to produce the second power in response to a supplemental power demand.

Abstract: In an example, a propulsion system for controlling maneuvers of a tilt rotor aircraft includes one or more processors and a non-transitory computer readable medium storing instructions that, when executed by the one or more processors, cause the propulsion system to perform functions. The functions include making a determination that changing an orientation of the tilt rotor aircraft is necessary to perform an instructed flight maneuver. The functions also include causing, in response to the determination, a rotor of the tilt rotor aircraft to provide a thrust, thereby applying a torque to the tilt rotor aircraft that changes the orientation of the tilt rotor aircraft.

Abstract: An aircraft is provided. The aircraft includes a ducted wing portion and a fan chamber. The fan chamber is attached to a bottom of the ducted wing portion. A fan assembly is provided in the fan chamber and is operative to blow air through the ducted wing portion. The ducted wing portion is configured to direct air blown by the fan assembly down to provide lift for the aircraft.

Abstract: An aircraft includes a wing that is extended through by a ducted fan having movable louvers.

Abstract: An exemplary tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode includes tiltable rotors located at forward boom ends, tiltable ducted fans located at wings aft of the forward boom ends, and aft rotors located on aft boom portions.

Abstract: A variable-sweep wing VTOL (vertical take-off and landing) aerial vehicle with distributed propulsion adapted for VTOL flight and horizontal flight includes a fuselage, a pair of symmetrical swiveling canards extending outward from forward portion of the fuselage, a pair of first symmetrical wings extending outward from the upper-rear portion of the fuselage and a pair of second symmetrical wings extending outward from the lower-rear portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joins the first wing and second wing at the tip to form the box-wing. The wings can transition between VTOL mode or airplane mode. The wings are mounted with rotors for propulsion. Moreover, at the trailing edge of the wings, the blown flap work as blown lift system for both VTOL flight or STOL flight. Finally, the fuselage mounted pusher rotor provides propulsive thrust for horizontal flight.

Abstract: Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

Abstract: An aircraft including a fuselage extending in an aircraft longitudinal direction, a wing coupled to the fuselage and extending in an aircraft lateral direction perpendicular to the aircraft longitudinal direction, and a displacement assembly configured to translate the wing relative to the fuselage in the aircraft lateral direction between a flight position and a stowed position. In the flight position, the displacement assembly is positioned at a central portion between opposite end portions of the wing such that the displacement assembly is positioned a first distance from one of the end portions of the wing. In the stowed position, the displacement assembly is positioned proximate one of the end portions of the wing such that the displacement assembly is positioned a second distance from the one of the end portions of the wing, the second distance being less than the first distance.

Abstract: A powered paragliding harness includes a harness with a pilot's back rest and an engine mount carrying a power unit with propeller. The back rest and engine mount are connected via at least first and second levers. Hinged connections connect one end of each to the back rest and the other end to the engine mount. The first lever is shorter than the second. In the harness operational state, the first lever is above the second. The levers enable the transition between an upright position, where the back rest—propeller angle is small, especially back rest and propeller are or close to parallel, for an upright pilot position during take-off/landing, and a reclined position, where the back rest—propeller angle is larger, for a reclined pilot position. The second lever—engine mount connection is nearer to the power unit center of gravity than the first lever—engine mount connection.

Abstract: Provided is a method for delivering goods through an unmanned aerial vehicle group including a plurality of aircraft respectively connected to delivery target goods. The method comprises identifying, by a master aircraft of the unmanned aerial vehicle group, an actual load applied to each of the aircraft by the goods while the unmanned aerial vehicle group is flying to deliver the goods, and controlling the unmanned aerial vehicle group by the master aircraft to adjust the actual load applied to each of the aircraft.

Abstract: An example UAV landing structure includes a landing platform for a UAV, a cavity within the landing platform, and a track that runs along the landing platform and at least a part of the cavity. The UAV may include a winch system that includes a tether that may be coupled to a payload. Furthermore, the cavity may be aligned over a predetermined target location. The cavity may be sized to allow the winch system to pass a tethered payload through the cavity. The track may guide the UAV to a docked position over the cavity as the UAV moves along the landing platform. When the UAV is in the docked position, a payload may be loaded to or unloaded from the UAV through the cavity.

Abstract: A trim actuator for a horizontal stabilizer comprises a power screw, a rotary actuator, configured to rotate the power screw, and a nut, configured to translate along the power screw when the power screw is rotated. Trim actuator also comprises an anti-back-drive mechanism, configured to prevent the power screw from rotating in a first rotational direction when a first force is applied to the nut in a first axial direction and to prevent the power screw from rotating in a second rotational direction, opposite the first rotational direction, when a second force is applied to the nut in a second axial direction. Trim actuator further comprises a sensor, configured to measure internal loading of the anti-back-drive mechanism when the first force is applied to the nut in the first axial direction or when the second force is applied to the nut in the second axial direction.

Abstract: Provided are methods of forming stiffened stringer panels with integrated plank structures. A skin member having an inner surface is provided. A plank is positioned onto the inner surface of the skin member. The plank extends from a first side to a second side, and each laminate ply of the set of layered laminate plies is sized to form a geometric profile for each of the first side and the second side. Each laminate ply of the set of layered laminate plies is arranged to extend from the first side to the second side. A stringer is placed onto a support tool. The support tool, and the stringer thereon, is positioned upon an uppermost laminate ply of the set of layered laminate plies. The skin member, the plank, and the stringer are joined.

Abstract: A hinge mechanism for hingedly coupling a flight control member having a top surface to an aircraft component having a top surface includes a first hinge member pivotably coupled to the flight control member about a first axis and slidingly coupled to the aircraft component and a second hinge member pivotably coupled to the aircraft component about a second axis and slidingly coupled to the flight control member. The first hinge member is pivotably coupled to the second hinge member about a central axis. The first hinge member and the second hinge member are configured to cooperatively facilitate movement the flight control member relative to the aircraft component between at least a stowed position and a deployed position.

Abstract: A leading-edge component for an aircraft includes at least a part of a flow body having a front skin and a rib. The front skin comprises a top section, a bottom section and a leading edge arranged therebetween. The rib extends from the bottom section to the top section. The rib comprises a flange that at least partially surrounds the rib. The flange is attached to an inner side of the front skin. The at least one peripheral surface extends from the contact surface inwardly into the flow body and away from the inner side of the front skin or encloses a weakened connection region with the contact surface for bending inwardly into the flow body upon an impact onto the front skin on or adjacent to the at least one peripheral surface.

Abstract: An aircraft wing and propulsion system includes a leading-edge device positioned at the leading edge of an aircraft wing and one or more propulsors affixed to the main body of the aircraft wing. The leading-edge device includes a moveable slat affixed to the aircraft wing with an extension mechanism such that the moveable slat is translatable between a closed position abutting a main body of the aircraft wing and an open position extended from the main body of the aircraft wing to form a gap. An associated method of operating the same during takeoff and landing includes extending the moveable slat to expose the propulsors on the aircraft wing and operating the propulsors during take-off or landing of the aircraft to provide increased power and lift for the aircraft.

Abstract: A lavatory for an aircraft cabin includes a wall having a forward wall portion disposed immediately aft of and substantially conforming to an exterior aft surface of an aircraft cabin structure, such as a passenger seat, that is substantially not flat in a vertical plane. The forward wall portion includes a forward projection over an aft portion of the adjacent passenger seat. The forward wall portion can define a secondary space in the interior lavatory space, which can provide an amenity stowage space, and can include design elements providing visual space.

Abstract: An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.

Abstract: A load carrying assembly for carrying a load with a rotary wing aircraft. The load carrying assembly includes a cargo cable and a load engaging system. The cargo cable may have a first end that is attachable to a hoist or a cargo hook arrangement. The load engaging system may include a first attachment that is attached to the second end of the cargo cable, a second attachment that is adapted for receiving a load, a connecting apparatus that connects the first attachment with the second attachment, and at least two first and second thrust producing devices that are attached to the connecting apparatus and produce thrust in a direction that is orthogonal to the cargo cable extension.

Abstract: There is provided a drone system in which a drone and a movable body operate in coordination with each other, the movable body being capable of moving with the drone aboard and allowing the drone to make a takeoff and a landing, the movable body including: a takeoff-landing area on which the drone can be placed and that serves as a takeoff-landing point from and on which the drone takes off and lands; a movement control section capable of moving the movable body together with the drone aboard; and a movable body transmission section that sends information on the movable body, the drone including: a flight control section that causes the drone to fly; and a drone reception section that receives information on the movable body, wherein the drone sends, to the movable body, a position of a takeoff-landing point at a time when the drone takes off.

Abstract: A device for securing at least one sling for transporting a load under a helicopter, the securing device comprising at least a first strap and at least a second strap, a connection mechanism configured, in the closed state, to connect the straps, to form a comprehensive security strap capable of supporting a sling and, in the open state, to release the straps for releasing the sling, and an actuator configured to open the connection mechanism following a mechanical effort being introduced, the connection mechanism comprising cascading reduction means configured to reduce the resistance force during the opening of the connection mechanism generated by the load connected to the sling.